EP3055207B1 - Système et procédé de mesure d'angle de battement d'hélicoptère - Google Patents

Système et procédé de mesure d'angle de battement d'hélicoptère Download PDF

Info

Publication number
EP3055207B1
EP3055207B1 EP13895430.0A EP13895430A EP3055207B1 EP 3055207 B1 EP3055207 B1 EP 3055207B1 EP 13895430 A EP13895430 A EP 13895430A EP 3055207 B1 EP3055207 B1 EP 3055207B1
Authority
EP
European Patent Office
Prior art keywords
sensor
flapping
helicopter
signal
hub
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP13895430.0A
Other languages
German (de)
English (en)
Other versions
EP3055207A4 (fr
EP3055207A1 (fr
Inventor
Magnus BERGELIN
Kristian ERLANDSSON
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Ums Skeldar Sweden AB
Original Assignee
Ums Skeldar Sweden AB
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Ums Skeldar Sweden AB filed Critical Ums Skeldar Sweden AB
Publication of EP3055207A1 publication Critical patent/EP3055207A1/fr
Publication of EP3055207A4 publication Critical patent/EP3055207A4/fr
Application granted granted Critical
Publication of EP3055207B1 publication Critical patent/EP3055207B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
    • G01D5/00—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable
    • G01D5/12—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable using electric or magnetic means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/008—Rotors tracking or balancing devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/37—Rotors having articulated joints
    • B64C27/39—Rotors having articulated joints with individually articulated blades, i.e. with flapping or drag hinges
    • G—PHYSICS
    • G07—CHECKING-DEVICES
    • G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
    • G07C5/00—Registering or indicating the working of vehicles
    • G07C5/08—Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle or waiting time
    • G07C5/0808—Diagnosing performance data
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B64D2045/0085—Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/17—Helicopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/40—Ornithopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/70—Constructional aspects of the UAV body
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U40/00—On-board mechanical arrangements for adjusting control surfaces or rotors; On-board mechanical arrangements for in-flight adjustment of the base configuration
    • B64U40/10—On-board mechanical arrangements for adjusting control surfaces or rotors; On-board mechanical arrangements for in-flight adjustment of the base configuration for adjusting control surfaces or rotors

Definitions

  • the invention relates in general to a method for monitoring movements of the rotor blades attached by flapping hinges to a rotor head or hub of a helicopter, and where the flapping hinges permit vertical angular displacement of the blades relative to the rotor head/hub, and to a helicopter comprising a corresponding system.
  • the present invention is based on the design of a device or a system including linear position transducers (LDT) by which it is possible to monitor and calculate when and how much the, for instance two, rotor blades are "flapping" upwards.
  • LDT linear position transducers
  • a rotor blade is "flapping" with about the same frequency as the rotor speed, allowing the signal to come out from the system as a sine curve.
  • the flapping frequency depends on the rotor configuration and some parameters for example the flapping hinge offset from the rotor center of rotation
  • US2620888 illustrates for example a system that indicates and corrects the unbalance in the lifting force of the rotors of a helicopter.
  • the document describes a mechanism that detects differences in the flapping between the rotors, and then compensates the flapping behavior by means of a hydraulic system. This mechanism does not for instance include any electronic or linear sensors.
  • US2936836 illustrates a rotor blade tracking mechanism for lifting rotors of a helicopter and the purpose of the invention is to indicate and correct for lifting differences between the rotors in order to minimize undesirable vibrations.
  • the document describes a system that detects unbalance in the flapping behavior between the rotors. This is based on that the angle between the rotors is changed and the system makes use of that the flapping hinges generate sinus wave formed motions.
  • WO20120953325 describes a function-monitored guidance system, a high-lift system, with a monitoring device providing operating state determination function for determining overshoots of stored threshold values.
  • the invention illustrates surveillance of components in order to discover wear, primarily at interceptor aircraft in which sensors measure the mechanical properties such as load states of a component like a flapper point or a bearing and compare these values with desired predetermined values.
  • the sensors measures for example vibrations, acceleration or tension.
  • US 2011/0027082 A1 relates to reducing the vibration of a lift and propulsion rotor of a rotorcraft, the rotor having a plurality of airfoil assemblies that perform rotary movement around a drive axis of the rotor, each airfoil assembly comprising a blade extending longitudinally from a root suitable for being fastened to hinge means of a hub of said rotor.
  • An angle sensor suitable for giving information relating to the absolute value of the flapping angle of the blade is provided.
  • One object of the present invention is to solve the problems indicated above and to create a helicopter comprising a flap angle measurement system and a method that is effective, simple in its design and reliable to use and that measures the angular change of the flapping hinge for each rotor blade in the rotor head/hub of the helicopter.
  • a further object is to provide the helicopter with a system including a new and efficient mechanical/electrical device, which effectively is able to monitor the angular change of the flapping hinge and generate an electrical signal related to the angular change.
  • a further object of the invention is that the system should be simple in its design and consist of as few parts as possible and thus be cost effective to manufacture and install.
  • a further object of the invention is that the system should be of low weight and compact in size.
  • a further object of the present invention is that the system should be easy to adjust/calibrate.
  • the invention relates, as indicated above, to a helicopter and method for monitoring vertical movements of the rotor blades attached by flapping hinges to a central head/hub of a helicopter.
  • the invention is achieved according to claims 1 and 8, by designing the system so that at least one sensor is arranged to continuously measure the vertical angular movement of the flapping hinge.
  • the simple design of the invention results in that at least one sensor is arranged to continuously measure the vertical angular movement of the flapping hinge.
  • the at least one sensor one sensor per rotor blade, is arranged to generate an electrical signal that is a sine wave as long as all parts are functioning as expected.
  • a control/evaluation unit is arranged to receive the electrical signal from the sensor and evaluate the signal for detecting any abnormalities.
  • the control/evaluation unit may be arranged to compare the actual measured electrical signal to a stored signal or value in order to detect if the actual measured signal depart from the predetermined signal or from predetermined acceptable values, i.e. there is detected if the actual measured signal is distorted in any way, indicating that the flapping hinge is malfunctioning and/or needs maintenance.
  • This monitoring system/method can be used as a simple and effective tool during flight in an operational helicopter for constantly/continuously monitoring e.g. the wear of bearings and/or other components in the rotor head/hub.
  • the system/device can also preferably be used as an effective tool for evaluation and checking of the condition of new rotor head/hub designs.
  • Figure 1a,b illustrates in principle the flapping movement that may occur for a rotor blade 1 on a helicopter (not shown) during flight.
  • the rotor blade 1 is moving/flapping around a flapping hinge 2, the movment is indicated by an arrow 3.
  • the flapping comes from cyclic pitch command i.e. if the pilot wants to put the helicopter in forward flight for example.
  • the flapping also comes from winds/gust.
  • the allowance of blade flapping will reduce bending forces in the rotor blades and is a common design in helicopters.
  • FIG 2 illustrates from the side a rotor head/hub 4 located on the top of a helicopter rotor shaft 5.
  • the head/hub 4 has a main body and connecting members projecting from the main body and for e.g. the connection of respective blade (not shown).
  • the main body and the connecting members being defined by separate components connectable to one another by releasable fastening means like bolts for example.
  • the helicopter may typically be of e.g. the type of VTOL ("Vertical Take Off and Landing") and/or UAV ("Unmanned Aerial Vehicle”).
  • the rotor blades are normally mounted to the rotor shaft or head/hub via a rotor blade linkage 6.
  • the flapping of the rotor blades is made possible by the means of flapping hinges 7 and the rotor blades are thereby able to partly rotate in their vertical directions, (as indicated by the arrow 8).
  • the LDT is fixed to the rotor head 4 by screws/bolts and a console 10.
  • the sensor arm or axle 11 of the LDT is adjustable by an adjustment mechanism 12, formed like a washer which is possible to adjust by screwing.
  • the sensor axle 11 is in contact with a tilting washer 13 that rotates with the flapping hinge 7 together with the rotor blade when the rotor blade turns upwards or downwards. It is important that the axle 11 of the sensor 9, the linear position transducer, always is in mechanical contact with the tilting washer 13 and this adjustment could be made by the help of the adjustment mechanism 12.
  • both sensors 9 may by calibrated to each other in order to give exactly the same response, the same electrical signals or the same signal values, at a given flapping angle ⁇ of the rotor blades.
  • FIG. 3 illustrates more in detail the sensors 9 and their installation on the rotor head 4.
  • the sensors 9 are mounted by means of screws and consoles 10.
  • Each sensor 9 is arranged with a central axle 11 that moves longitudinally within the sensor 9.
  • the axle 11 is in contact with the tilting washer 13 via a heel 15 and moves thereby in accordance with the flapping hinge 7 and the tilting washer 13.
  • the sensor 9, and its axle 11, may be mechanically adjusted in its length position by an adjustment mechanism 12 located in the console 10.
  • the mechanical adjustment is performed by manually rotating the adjustment mechanism 12 which may be provided with a thread and a washer formed element. After the adjustment the sensor 9 is locked in its new position by e.g. a screw 16.
  • the control/evaluation unit 14 is arranged to receive the electrical signal and evaluate the signal in order to detect any abnormalities in the normally sine wave formed signal by comparing the actual measured electrical signal to a stored signal or stored value in order to detect if the actual measured signal depart from the predetermined and acceptable values, i.e. if the actual signal is distorted in any way, indicating that the flapping hinge 7 or the rotor blade is malfunctioning and/or needs maintenance.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Toys (AREA)

Claims (11)

  1. Hélicoptère avec des pales de rotor attachées par des charnières battantes (7) à une tête centrale (4) ou un moyeu, l'hélicoptère comprenant un système de surveillance de mouvements dans les pales de rotor,
    caractérisé en
    ce que le système comprend au moins un capteur (9) installé sur la tête centrale (4) ou le moyeu, et dans lequel un axe de capteur (11) de l'au moins un capteur (9) est en contact avec une rondelle d'inclinaison (13) qui tourne avec une charnière battante (7) desdites charnières battantes (7), dans lequel l'axe de capteur (11) est configuré de manière à se déplacer longitudinalement au sein de l'au moins un capteur (9), en conformité avec le mouvement de la rondelle d'inclinaison (13), et dans lequel l'au moins un capteur (9) est agencé de manière à mesurer en continu le mouvement angulaire vertical (α) de la charnière battante (7).
  2. Hélicoptère selon la revendication 1,
    caractérisé en
    ce que l'au moins un capteur (9) est agencé pour générer un signal électrique.
  3. Hélicoptère selon la revendication 1 ou 2,
    caractérisé en
    ce que l'au moins un capteur (9) est un capteur linéaire, de préférence un transducteur dit de position linéaire ou LDT.
  4. Hélicoptère selon l'une quelconque des revendications précédentes,
    caractérisé en
    ce que l'au moins un capteur (9) mesure le mouvement angulaire vertical (α) de la charnière battante (7) pendant toute la rotation d'un arbre de rotor (5) au sommet duquel est située la tête centrale ou le moyeu (4).
  5. Hélicoptère selon la revendication 2,
    caractérisé en
    comprenant en outre
    une unité de commande / évaluation (14) agencée pour recevoir le signal électrique et l'évaluer pour détecter toute anomalie dans le fonctionnement mécanique.
  6. Hélicoptère selon l'une quelconque des revendications précédentes,
    caractérisé en
    ce que l'au moins un capteur (9) génère normalement un signal qui est un signal formé par une onde sinusoïdale.
  7. Hélicoptère selon la revendication 5,
    caractérisé en
    ce que l'unité de commande / évaluation (14) est agencée pour comparer le signal électrique mesuré réel à un signal ou à une valeur stockée afin de détecter si le signal mesuré réel part des valeurs prédéterminées et acceptables, c'est-à-dire si le signal réel est déformé de quelque façon que ce soit, indiquant que la charnière battante présente un dysfonctionnement et / ou nécessite un entretien.
  8. Procédé de surveillance des mouvements des pales de rotor fixées par des charnières battantes (7) à une tête centrale (4) ou à un moyeu d'un hélicoptère,
    caractérisé par
    la mesure continue au moyen d'un capteur (9) d'un mouvement angulaire vertical (α) d'une charnière battante (7) desdites charnières battantes (7),
    dans lequel le capteur (9) est installé sur la tête centrale (4) ou le moyeu, et dans lequel un axe de capteur (11) du capteur (9) est en contact avec une rondelle d'inclinaison (13) qui tourne avec une charnière battante (7), et dans lequel l'axe de capteur (11) est configuré de manière à se déplacer longitudinalement au sein de l'au moins un capteur (9), en conformité avec le mouvement de la rondelle d'inclinaison (13).
  9. Procédé selon la revendication 8,
    caractérisé par
    la génération en continu d'un signal électrique en réponse au mouvement angulaire (α) d'une pale de rotor et / ou de la charnière battante (7).
  10. Procédé selon la revendication 9,
    caractérisé par
    l'évaluation du signal électrique pour détecter toute anomalie dans le fonctionnement mécanique.
  11. Procédé selon l'une quelconque des revendications 9 à 10,
    caractérisé par
    la comparaison du signal électrique mesuré réel à un signal ou à une valeur stocké(e) afin de détecter si le signal mesuré réel part des signaux / valeurs prédéterminés et acceptables, c'est-à-dire si le signal réel est déformé de quelque façon que ce soit, indiquant que la charnière battante (7) présente un dysfonctionnement et / ou nécessite un entretien.
EP13895430.0A 2013-10-10 2013-10-10 Système et procédé de mesure d'angle de battement d'hélicoptère Active EP3055207B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/SE2013/051192 WO2015053671A1 (fr) 2013-10-10 2013-10-10 Système et procédé de mesure d'angle de battement

Publications (3)

Publication Number Publication Date
EP3055207A1 EP3055207A1 (fr) 2016-08-17
EP3055207A4 EP3055207A4 (fr) 2017-06-21
EP3055207B1 true EP3055207B1 (fr) 2018-10-03

Family

ID=52813398

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13895430.0A Active EP3055207B1 (fr) 2013-10-10 2013-10-10 Système et procédé de mesure d'angle de battement d'hélicoptère

Country Status (4)

Country Link
US (1) US9897462B2 (fr)
EP (1) EP3055207B1 (fr)
ES (1) ES2703140T3 (fr)
WO (1) WO2015053671A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107140202B (zh) * 2017-05-12 2023-06-20 郑可为 一种离心式挥舞铰旋翼头
CN112407323B (zh) * 2020-11-03 2022-07-01 中国直升机设计研究所 一种铰接式旋翼桨根运动参数测量装置及方法
CN113138068B (zh) * 2021-03-31 2023-09-05 中国飞机强度研究所 一种襟翼运动机构疲劳试验装置及其方法
US20240327013A1 (en) * 2023-03-31 2024-10-03 Beta Air, Llc System for controlling a propulsor assembly of an electric aircraft

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2620888A (en) 1947-03-10 1952-12-09 Harold T Avery Blade tracking mechanism for lifting rotors
US2936836A (en) 1956-06-01 1960-05-17 Kaman Aircraft Corp Mechanism for indicating and correcting lift differences in helicopter rotors
US3954229A (en) * 1975-01-02 1976-05-04 Textron, Inc. Automatic one-per-rev control system
US4246967A (en) * 1979-07-26 1981-01-27 The Dow Chemical Company Cementing head apparatus and method of operation
US4519743A (en) * 1980-03-21 1985-05-28 Massachusetts Institute Of Technology Helicopter individual blade control system
US4667158A (en) * 1985-04-01 1987-05-19 Redlich Robert W Linear position transducer and signal processor
GB8810214D0 (en) * 1988-04-29 1988-06-02 Lucas Ind Plc Movement transducer
DE19804717C2 (de) * 1997-01-17 2002-08-08 Eurocopter Deutschland Mehrblattrotor
JP2878229B2 (ja) * 1997-03-21 1999-04-05 株式会社コミュータヘリコプタ先進技術研究所 回転翼機用接地センサ
US6415206B1 (en) * 2000-02-24 2002-07-02 Simmonds Precision Products, Inc. Method for determining a minimal set of rotor blade adjustments
ITBO20000356A1 (it) * 2000-06-16 2001-12-16 Gd Spa Metodo e dispositivo di prelievo di pile di sbozzati .
JP3638257B2 (ja) * 2001-04-13 2005-04-13 川崎重工業株式会社 回転翼航空機の揺動制御装置および方法
JP3728242B2 (ja) * 2001-12-21 2005-12-21 防衛庁技術研究本部長 回転翼航空機のロータの揺動制御装置
FR2948631B1 (fr) * 2009-07-28 2012-01-27 Eurocopter France Procede pour reduire voire supprimer les vibrations d'un rotor de sustentation et de propulsion d'un giravion, ainsi qu'un ensemble aerodynamique et un rotor mettant en oeuvre ledit procede
DE102011008561A1 (de) 2011-01-14 2012-07-19 Airbus Operations Gmbh Funktionsüberwachtes Führungssystem zur Verstellung zumindest einer Systemkomponente sowie Verfahren zur Funktionsüberwachung eines solchen Führungssystems
CN103827525A (zh) 2011-04-07 2014-05-28 洛德公司 装有运动控制轴承的旋翼式飞机
US8496199B2 (en) * 2011-07-12 2013-07-30 Textron Innovations Inc. System and method for limiting cyclic control inputs
WO2013009303A1 (fr) * 2011-07-12 2013-01-17 Bell Helicopter Textron Inc. Affichage de marge de contrôle cyclique de pilotage
FR2981045B1 (fr) * 2011-10-10 2013-10-25 Eurocopter France Systeme de pilotage en lacet pour giravion, mettant en oeuvre un organe entraine par l'homme qui genere des commandes de vol par objectif
FR2988075B1 (fr) * 2012-03-19 2014-04-25 Eurocopter France Dispositif de surveillance du comportement en battement et/ou en trainee d'une pale de rotor d'un giravion

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
ES2703140T3 (es) 2019-03-07
US9897462B2 (en) 2018-02-20
EP3055207A4 (fr) 2017-06-21
WO2015053671A1 (fr) 2015-04-16
EP3055207A1 (fr) 2016-08-17
US20160282140A1 (en) 2016-09-29

Similar Documents

Publication Publication Date Title
EP3344870B1 (fr) Éolienne et procédé de fonctionnement d'éolienne ayant une zone d'exclusion de vitesse de rotation
EP2905224B1 (fr) Système de détection d'état de rotor
US10301038B2 (en) System and method for detecting mechanical failure in the high lift system of an aircraft
EP3055207B1 (fr) Système et procédé de mesure d'angle de battement d'hélicoptère
US4519743A (en) Helicopter individual blade control system
US11085416B2 (en) Electrical pitch control system and a method for operating at least one rotor blade and use of the system for performing the method
US9481456B2 (en) Relative acceleration blade position measurement
WO2016137566A1 (fr) Estimation harmonique de jeu d'extrémité
US20240343388A1 (en) Tilt rotor control
US11952111B2 (en) Electronic control of blade pitch on a tiltrotor
EP3476722B1 (fr) Contrôle de la stabilité au tourbillonnement des volets d'un rotor basculant comportant une rétroaction de cisaillement du moyeu pour aéronef à grande vitesse
EP3196119B1 (fr) Giravion et système et procédé associés de surveillance de position de pale de rotor
US11059570B2 (en) Movable flight surface having at least one integrated actuator
KR20230007233A (ko) 풍력 터빈의 방위각 센서
EP2976260B1 (fr) Compensation du mouvement de traînée dans un système de rotor
US11084572B2 (en) Electromechanical actuator for a movable flight surface
JP3600151B2 (ja) 回転翼航空機の突風制御装置
KR20130097279A (ko) 비행체 로터 출력 보정 시스템
US20190344882A1 (en) Blade moment adjustment system

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20160428

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: UMS SKELDAR SWEDEN AB

DAX Request for extension of the european patent (deleted)
A4 Supplementary search report drawn up and despatched

Effective date: 20170519

RIC1 Information provided on ipc code assigned before grant

Ipc: B64C 27/39 20060101AFI20170515BHEP

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

RIC1 Information provided on ipc code assigned before grant

Ipc: B64C 27/39 20060101AFI20180314BHEP

Ipc: B64D 45/00 20060101ALN20180314BHEP

GRAJ Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

REG Reference to a national code

Ref country code: DE

Ref legal event code: R079

Ref document number: 602013044694

Country of ref document: DE

Free format text: PREVIOUS MAIN CLASS: B64C0027320000

Ipc: B64C0027390000

RIC1 Information provided on ipc code assigned before grant

Ipc: B64C 27/39 20060101AFI20180320BHEP

Ipc: B64D 45/00 20060101ALN20180320BHEP

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20180411

INTC Intention to grant announced (deleted)
INTG Intention to grant announced

Effective date: 20180508

RIC1 Information provided on ipc code assigned before grant

Ipc: B64D 45/00 20060101ALN20180423BHEP

Ipc: B64C 27/39 20060101AFI20180423BHEP

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: AT

Ref legal event code: REF

Ref document number: 1048318

Country of ref document: AT

Kind code of ref document: T

Effective date: 20181015

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602013044694

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20181003

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2703140

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20190307

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181003

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181003

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181003

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181003

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190103

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181003

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190203

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181003

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181003

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190103

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190104

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181003

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190203

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181003

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20181031

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181010

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602013044694

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181003

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181003

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

REG Reference to a national code

Ref country code: AT

Ref legal event code: UEP

Ref document number: 1048318

Country of ref document: AT

Kind code of ref document: T

Effective date: 20181003

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181003

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181031

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181031

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181003

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181003

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181003

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181003

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181031

26N No opposition filed

Effective date: 20190704

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20190103

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181003

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181010

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190103

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181010

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181003

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181003

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20131010

Ref country code: MK

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181003

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20221014

Year of fee payment: 10

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 20221017

Year of fee payment: 10

Ref country code: ES

Payment date: 20221101

Year of fee payment: 10

Ref country code: DE

Payment date: 20221019

Year of fee payment: 10

Ref country code: AT

Payment date: 20221020

Year of fee payment: 10

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602013044694

Country of ref document: DE

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1048318

Country of ref document: AT

Kind code of ref document: T

Effective date: 20231010

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20231010

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20231031

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240501

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20231010

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20231011